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Effect of microramps on flare-induced shock – boundary-layer interaction

  • T. Nilavarasan (a1), G. N. Joshi (a1) and A. Misra (a1)


The ability of microramps to control shock - boundary layer interaction at the vicinity of an axisymmetric compression corner was investigated computationally in a Mach 4 flow. A cylinder/flare model with a flare angle of 25° was chosen for this study. Height (h) of the microramp device was 22% of the undisturbed boundary layer thickness (δ) obtained at the compression corner location. A single array of these microramps with an inter-device spacing of 7.5h was placed at three different streamwise locations viz. 5δ, 10δ and 15δ (22.7h, 45.41h and 68.12h in terms of the device height) upstream of the corner and the variations in the flowfield characteristics were observed. These devices modified the separation bubble structure noticeably by producing alternate upwash and downwash regions in the boundary layer. Variations in the separation bubble’s length and height were observed along the spanwise (circumferential) direction due to these devices.


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1. Vishwanath, P.R. Shock-wave turbulent boundary-layer interaction and its control: a survey of recent developments, Sadhana, 1988, 12, (1), pp 45104.
2. Delery, J.M. Shock wave/turbulent boundary layer interaction and its control, Progress in Aerospace Sciences, 1985, 22, (4), pp 209280.
3. Dolling, D.S. Fifty years of shock-wave/boundary-layer interaction research: what next?, AIAA Journal, 2001, 39, (8), pp 15171531.
4. Kistler, A.L. Fluctuating wall pressure under a separated supersonic flow, The Journal of the Acoustical Society of America, 1964, 36, (3), pp. 543550.
5. Kuehn, D.M. Laminar boundary-layer separation induced by flares on cylinders at zero angle of attack, Technical Report R-146, 1961.
6. Settles, G.S. and Bogdonoff, S.M. Separation of a supersonic turbulent boundary layer at moderate to high Reynolds numbers, 1973, AIAA Paper, pp 666.
7. Roshko, A. and Thomke, G.J. Flare-induced interaction lengths in supersonic, turbulent boundary layers, AIAA Journal, 1976, 14, (7), pp 873879.
8. Heffener, K.S., Chpoun, A. and Lengrand, J.C. Experimental study of transitional axisymmetric shock-boundary layer interactions at Mach 5, 23rd Fluid Dynamics, Plasmadynamics and Lasers Conference, 1993, AIAA Paper, pp 3131.
9. Babinsky, H and Edwards, J.A. On the incipient separation of a turbulent hypersonic boundary layer, The Aeronautical Journal, 1996, 100, (996), pp 209214.
10. Kontis, K and Stollery, J.L. Incipient separation on flared bodies at hypersonic speeds, The Aeronautical Journal, 1999, 103, (1027), pp 405414.
11. Kontis, K. Flow control effectiveness of jets, strakes and flares at hypersonic speeds, Proceedings of the Institution of Mech Engineers, Part G: J of Aerospace Engineering, 2008, 222, (5), pp 585603.
12. Settles, G.S., Bogdonoff, S.M. and Vas, I.E. Incipient separation of a supersonic turbulent boundary layer at high Reynolds numbers, AIAA Journal, 1976, 14, (1), pp 5056.
13. Taylor, G.I. and Maccoll, J.W. The air pressure on a cone moving at high speeds – I, Proceedings of the Royal Society of London Series A, 1933, 139, (838), pp 278297.
14. Coleman, G.T. and Stollery, J.L. Incipient separation of axially symmetric hypersonic turbulent boundary layers, AIAA Journal, 1973, 12, (1), pp 119120.
15. Maull, D.J. Hypersonic flow over axially symmetric spiked bodies, Journal of Fluid Mechanics, 1960, 4, pp 584592.
16. Verma, S.B. and Koppenwallner, G. Unsteady separation in flare-induced hypersonic shock-wave-boundary-layer interaction flowfield, Journal of Spacecrafts and Rockets, 2002, 39, (3), pp 467470.
17. Priebe, S. and Martin, M.P. Low-frequency unsteadiness in shock wave turbulent boundary layer interaction, Journal of Fluid Mechanics, 2012, 699, pp 149.
18. Verma, S.B. and Hadjadj, A. Supersonic flow control, Shock Waves, 2015, 25, (5), pp 443449.
19. Szwaba, R. Comparison of influence of different air-jet vortex generators on the separation region, Aerospace Science and Technology, 2011, 15, (1), pp 4552.
20. Chidambaranathan, M., Verma, S.B. and Rathakrishnan, E. Control of incident shock-induced boundary-layer separation using steady microjet actuators at Mα = 3.5, Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2019, 223, (4), pp 12841306.
21. Uzun, A., Solomon, J.T., Foster, C.H., Oates, W.S., Hussaini, M.Y. and Alvi, F.S. Flowphysics of a pulsed microjet actuator for high-speed flow control, AIAA Journal, 2013, 51, (12), pp 28942918.
22. Narayanaswamy, V., Raja, L.L. and Clemens, N.T. Characterization of a high-frequency pulsed-plasma jet actuator for supersonic flow control, AIAA Journal, 2010, 48, (2), pp 297305.
23. Deshpande, A.S. and Poggie, J. Flow control of swept shock-wave/boundary-layer interaction using plasma actuators, Journal of Spacecrafts and Rockets, 2018, 55, (5), pp 110.
24. Bruce, P.J.K. and Colliss, S.P. Review of research into shock control bumps, Shock Waves, 2015, 25, (5), pp 451471.
25. Sriram, R. and Jagadeesh, G. Shock tunnel experiments on control of shock induced large separation bubble using boundary layer bleed, Aerospace Science and Technology, 2014, 36, (7), pp 8793.
26. Su, C., Li, Y., Cheng, B., Wang, J. and Cao, J. MHD flow control of oblique shock waves around ramps in low-temperature supersonic flows, Chinese Journal of Aeronautics, 2010, 23, (1), pp 2232.
27. Lu, F.K., Li, Q. and Liu, C. Microvortex generators in high speed flow, Progress in Aerospace Sciences, 2012, 53, pp 3045.
28. Panaras, A.G. and Lu, F.K. Micro-vortex generators for shock wave/boundary layer interactions, Progress in Aerospace Sciences, 2015, 74, pp 1647.
29. Titchener, N. and Babinsky, H. A review of the use of vortex generators for mitigating shock-induced separation, Shock Waves, 2015, 25, (5), pp 473494.
30. Bur, R., Coponet, D. and Carpels, Y. Separation control by vortex generator devices in a transonic flow, Shock Waves, 2009, 19, (6), pp 521530.
31. Babinsky, H., Makinson, N.J. and Morgan, C.E. Micro-vortex generator flow control for supersonic engine inlets, 2007, AIAA Paper, pp 521.
32. Babinsky, H., Li, Y. and Pitt Ford, C.W. Microramp control of supersonic oblique shock-wave/boundary-layer interactions, 2009, AIAA Journal, 47, (3), pp 668675.
33. Holden, H.A., and Babinsky, H. Vortex generators near shock/boundary layer interactions, 42nd AIAA Aerospace Sciences Meeting, 2004, AIAA Paper, pp 1242.
34. Barter, J.W. and Dolling, D.S. Reduction of fluctuating pressure loads in shock/boundary layer interactions using vortex generators, AIAA Journal, 1995, 33, (10), pp 18421849.
35. Lee, S., Loth, E. and Babinsky, H. Normal shock boundary layer control with various vortex generator geometries, Computer and Fluids, 2011, 49, pp 233246.
36. Martis, R.R. and Misra, A. Separation attenuation in swept shock wave-boundary layer interactions using different micro vortex generator geometries, Shock Waves, 2017, 27, (5), pp 747760.
37. Verma, S.B. and Manisankar, C. Assessment of various low-profile mechanical vortex generators in controlling a shock induced separation, AIAA Journal, 2017, 55, (7), pp 113.
38. Verma, S.B. and Manisankar, C. Control of incident shock-induced separation using vane-type vortex generating devices, AIAA Journal, 2018, 56, (4), pp 16001615.
39. Lee, S. and Loth, E. On ramped vanes to control normal shock-boundary layer interactions, The Aeronautical Journal, 122, (1256), 2018, pp 118.
40. Martis, R.R., Misra, A. and Singh, A. Effect of microramps on separated swept-shock wave-boundary layer interactions, AIAA Journal, 2014, 52, (3), pp 591603.
41. Ashill, P.R., Fulker, J.L. and Hackett, K.C. A review of recent developments in flow control, The Aeronautical Journal, 2005, 109, (1095), pp 205232.
42. Nolan, W.R. and Babinsky, H. Comparison of micro-vortex generators in supersonic flows, 6th AIAA Flow Control Conference, 2012, AIAA Paper, pp 2812.
43. Xue, D.W., Chen, Z.H., Jiang, X.H. and Fan, B.C. Numerical investigations on the wake structures of micro-ramp and micro-vanes, Fluid Dynamics Research, 2014, 46, (1), pp 015505.
44. Rybalko, M., Babinsky, H. and Loth, E. VGs for a normal SBLI with a downstream diffuser, 40th Fluid Dynamic Conference and Exhibit, 2010, AIAA Paper, pp 4464.
45. Geipman, R.H.M., Schrijer, F.F.J. and van Oudheusden, B.W. Flow control of an oblique shock wave reflection with micro-ramp vortex generators: effect of location and size, Physics of Fluids, 26, 2014, 066101.
46. Titchener, N. and Babinsky, H. Shock wave/boundary-layer interaction control using a combination of vortex generators and bleed, AIAA Journal, 2013, 51, (5), pp 12211233.
47. Vaisakh, S. and Muruganandam, T.M. Influence of multi-wall separation control on normal-shock-induced separation in supersonic duct flows, Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2019, 233, (9), pp 31843192.
48. Verma, S.B., Manisankar, C. and Raju, C. Control of shock unsteadiness in shock-boundary layer interaction on a compression corner using mechanical vortex generators, Shock Waves, 2012, 22, (4), pp 327339.
49. Yan, Y., Chen, L., Lee, Q. and Liu, C. Numerical study of micro-ramp vortex generator for supersonic ramp flow control at Mach 2.5, Shock Waves, 2017, 27, (1), pp 7996.
50. Estruch-Samper, D., Vanstone, L., Hillier, R. and Ganapathisubramani, B. Micro vortex generator control of axisymmetric high-speed laminar boundary layer separation, Shock Waves, 2015, 25, (5), pp 521533.
51. Liou, M.S. and Steffen, C.A. New flux splitting scheme, Journal of Computational Physics, 107, (1), 1993, pp. 2339.
52. Spalart, P.R. and Allmaras, S.R. A one-equation turbulence model for aerodynamic flows, 1992, AIAA Paper, pp 0439.
53. Anderson, B.H, Tinapple, J. and Surber, J. Optimal control of shock wave turbulent boundary layer interaction using micro array actuation, 2006, AIAA Paper, pp 3197.
54. Nilavarasan, T, Joshi, G.N., Misra, A., Manisankar, C. and Verma, S.B. Control of flare induced shock – boundary layer interaction using micro vortex generators, Proceedings of the 32nd International Symposium on Shock Waves, 2019, pp 27212738.
55. Herges, T., Kroeker, L., Elliot, G. and Dutton, C., Microramp flow control of normal shock/boundary-layer interactions, AIAA Journal, 48, (11), 2010, pp 25292542.
56. Edney, B. Anomalous heat transfer and pressure distributions on blunt bodies at hypersonic speeds in the presence of impinging shock, FFA Report, Aeronautical Research Institute of Sweden, 1968.
57. Delery, J. Three-dimensional separated flow topology: critical points, separation lines and vortical structures, John Wiley and Sons, Inc, 2013, USA.
58. Zheltovodov, A.A. and Knight, D.D. Ideal - gas shock wave – turbulent boundary - layer interactions in supersonic flows and their modelling: three - dimensional interactions, In Shock Wave – Boundary Layer Interactions, Babinsky, H. and Harvey, J.K. (Eds), Cambridge University Press, 2011, UK, pp 202258.
59. Tobak, M and Peake, D.J. Topology of three-dimensional separated flows, Annual Review of Fluid Mechanics, 1982, 14, pp 6185.
60. Lighthill, J.M. Attachment and separation in three-dimensional flow, In Laminar Boundary-Layer Theory, Rosenhead, L. (Ed), Oxford University Press, 1963, Oxford, UK, pp 7782.
61. Zheltovodov, A.A, Schulein, E.Kh and Yakovlev, V.N. Development of turbulent boundary layer at the conditions of mixed interaction with shock waves and expansion fans, ITAM USSR Academy of Sciences, 1983, Novosibirsk Preprint No: 28–83.
62. Grilli, M., Hickel, S and Adams, N.A. Large-eddy simulation of a supersonic turbulent boundary layer over a compression – expansion ramp, International Journal of Heat and Fluid Flow, 2013, 42, pp 7993.


Effect of microramps on flare-induced shock – boundary-layer interaction

  • T. Nilavarasan (a1), G. N. Joshi (a1) and A. Misra (a1)


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